| 摘要 |
The present invention relates to a trailing edge section (2) for a turbine blade (1). The trailing edge section comprises a first chamber (3,23) having at least one deformable wall (4); wherein the first chamber is adapted to collapse when a predetermined rotor speed is reached. In an embodiment, the trailing edge section further comprises a second chamber (26) arranged adjacent the first chamber (23), such that when the first chamber collapses, the second chamber is adapted to undergo a corresponding change in shape from an aerodynamic shape to a less aerodynamic shape.
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